EP3118124B1

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Info

Publication number: EP3118124B1
Application number: EP15002096.4A
Authority: EP
Inventors: Ulrich Knirsch
Original assignee: Airbus Defence and Space GmbH
Current assignee: Airbus Defence and Space GmbH
Priority date: 2015-07-15
Filing date: 2015-07-15
Publication date: 2021-05-12
Anticipated expiration: 2035-07-15
Also published as: US10179663B2; EP3118124A1; US20170015442A1

Description

The present invention relates to a landing device for a low gravity lander having a main body, wherein the low gravity lander comprises a number of legs. Furthermore, the invention relates to a low gravity lander.
Landing on a small body, like a comet, is particularly challenging. Even a very small impact velocity can lead to a rebound of the low gravity lander which might move the low gravity lander possibly back into deep space. Miniaturized landers cannot embark a reaction control system or a harpoon, as it was used by the low gravity lander Philae. Neither can miniaturized landers accommodate a full system of landing legs with a suspension as Philae had when landing on a comet. A simplified momentum absorption system would therefore be desirable.
Known landers have used airbags in the past. These need to be inflated at the right altitude. Hence, those landers require an altimeter. However, such altimeters are prone to malfunction. Airbags for use in space applications are also not trivial to test. For testing purposes, a vacuum chamber is required. The materials of the airbag are prone to aging and gas generators have a limited lifetime. The cost, mass and complexity are prohibitive, particularly for small landers, like low gravity landers.
Other landers have used a system of retro rockets and a sky crane lowering device. This system has a high complexity, resulting in a significant potential for contaminating a landing site.
To avoid a rebound upon landing on the landing site, the final impact velocity without having a momentum absorption device should be less than the local escape velocity. For small bodies, like low gravity landers, the velocity is in the order of several cm/s, i.e. a velocity already reached by a free fall from a small altitude. As a result, a landing device for the low gravity lander has to be deployed from a mother spacecraft extremely close to the surface of the landing site. This is inherently risky for the success of the low gravity lander or even the success of a whole mission because of the risk of the collision with the surface of the landing site. Thunder Tiger (thundertiger.com) offers a training gear for toy helicopters to be attached to the skid thereof with rubber band (XP55237275).
DocumentUS 5 265 829 A discloses an apparatus and a method for decelerating and absorbing impact of a re-entry vehicle. The apparatus includes four inflatable legs which are displaced equidistantly from each other around a capsule or housing containing a payload. Connected between each of the four legs are drag inducing surfaces that deploy as the legs inflate. The legs may bend upon impact. The present disclosure, on the other hand, contemplates rods attached to a common first side surface of the main body.
The same solution is also discussed in the following article: "CARBON-BASED ELECTRONICS", POPULAR MECHANICS, HEARST COMMUNICATIONS INC., NEW YORK, NY, US, Vol: 175, No. 4, 1 April 1998 (1998-04-01), Page: 24, XP000765650, ISSN: 0032-4558.
It is therefore an object of the present invention to provide a simplified landing device for a low gravity lander which enables secure and easy absorption of a momentum during landing on a landing site.
This object is solved by a landing device according toclaim 1. Preferred embodiments are set out in the dependent claims.
A landing device for a low gravity lander having a main body comprises a number of leg-like rods attached to the main body. In a deployment position of the rods, each of the number of rods is inclined with regard to a plane of a first side surface of the main body such that the rods substantially extend in a direction of movement of the low gravity lander. The number of rods is made such that they bend or buckle under forces within a predetermined range by an impact due to a landing on a landing surface (landing site), thereby absorbing an impact momentum.
A low gravity lander according to this description is a lander, which does not need to move after having landed on its target. The purpose of a low gravity lander is, for example, to measure data, collect and send them for evaluation purposes to an evaluation processing device (e.g. a satellite or a ground station). The target may be a comet. However, it may be any other planet or spacecraft device as well.
The landing device according to the invention is a simple, purely passive momentum absorption device. It consists of deployable rods that bend or buckle under the forces generated by the impact, thereby absorbing the momentum. In other words, the number of rods is transforming kinetic energy of the low gravity lander into heat. The landing device is vastly simpler, lighter and less costly than alternative landing devices as described above. The landing device may be implemented even on miniaturized landers. It tolerates all surface properties and most surface topologies.
Spacecrafts deploying such low gravity landers are no longer required to approach dangerously close to the target bodies.
According to a preferred embodiment, the number of rods is greater than three. In particular, the number of rods equals four. However, the number of rods can be greater than four as well.
The number of rods is attached to the first side surface of the main body. However, depending on a deployment mechanism, they may be attached to a sidewall adjacent to the first side surface as well.
Having at least three rods assigned to the first side surface, it can be assured that the low gravity lander can stand on his rods after having landed on the landing surface.
According to a further preferred embodiment, the length of the rods is determined as a function of the inclination angle with regard to the plane of the first side surface and an expected roughness of the landing surface such that no part of the landing surface is supposed to contact the main body. The expected surface roughness of the landing site can be determined before a mission of the low gravity lander. The feature "no part of the landing surface is supposed to contact the main body" is to be understood in that sense that no part of the surface is supposed to contact the body of the lander before the number of rods have bent or buckled.
The length of the rods may be determined as a function of the stowage space such that, in a stowage position, the rods do not extend beyond the first side surface of the main body. In particular, the length of the rods should be made such that each of the rods can be made from one piece, i.e. does not need a hinge to have the desired length of the rod.
According to a further improvement, the inclination angle of the number of rods is in a range between 120° and 150°, in particular 135°. It is preferred that the number of rods extends, in the deployment position, beyond the lateral edges of the first side surface.
The first side surface of the main body of the low gravity lander can be regarded as the front side of the low gravity lander which is directed to the landing side during a landing process.
The number of rods may be hollow. As an advantage, the total mass of the low gravity lander can be reduced. The lower the total mass of the low gravity lander is, the smaller is the impact momentum which is advantageous with regard to the rebound during landing.
The thickness and/or material of the number of rods may be determined as a function of the expected impact momentum. The expected impact momentum is the product of the total mass of the low gravity lander and the impact velocity. The higher the expected impact momentum is, the stiffer and/or thicker the number of rods should be made.
According to a further embodiment, a free end of at least some of the number of rods may be bent (i.e. may have the shape of a bow). Alternatively or in addition a free end of at least some of the number of rods may be fitted with a disc. These embodiments are in particular helpful where the expected landing surface consists of a soft terrain. However, in the case where the number of rods penetrates the soft terrain, this would absorb as much momentum as the rods are buckling or bending. Hence, the design of the number of rods can be made compliant with various surface properties.
According to a further preferred embodiment, in the stowing position, the number of rods is stowed above each other such that they substantially extend parallel to the plane of the first side surface. The number of rods may be assigned to a number of pairs of rods. By folding down one set (pair) of rods over the other, the space needed for stowage of the number of rods is small.
The number of rods may be deployable by a swiveling mechanism. The deployment may be made using the resilience of the rods themselves. In an alternative embodiment, the deployment may be made by an actuation member, such as a spring. Attachment of the number of rods to the main body of the low gravity lander may be made with help of a hinge. It is sufficient if a respective hinge has only one degree of freedom.
By folding down one set of rods over the other, all rods on the side surface of the main body of the low gravity lander can be secured or held down or locked by a single hold down device.
The landing device may comprise an activatable launch lock to prevent premature deployment, the launch lock being a time release device which enables a deployment of the number of rods from their stowage position to their deployment position upon a triggering event. Deployment of the number of rods has to be avoided before the ejection of the low gravity lander from a mother spacecraft. Here, the launch lock ensures the prevention of the premature deployment. The launch lock may be opened immediately prior to the ejection from the mother spaceship. In an embodiment, a time release device may be used to secure the number of rods for a predetermined time, e.g. in the order of some minutes. The time release device may be a bimetallic or shape memory alloy which is preheated (in the mother spaceship) before ejection and then frees the number of rods after cooling down.
The triggering event in this embodiment is the forthcoming ejection of the low gravity lander from the mother spacecraft.
According to a further preferred embodiment the main body comprises a second side surface being arranged opposite to the first side surface of the main body wherein a further number of leg-like rods is assigned to or attached to the second side surface. In this embodiment it is preferred if the inclination angle of all number of rods is 135° with regard to their assigned side surface. As a result, no knowledge about the impact direction of the low gravity lander has to be known since any side surface of a substantially cubic low gravity lander will be "protected" by a sufficient number of rods on which the low gravity lander can land.
The invention will be described in more detail by reference to the accompanying figures.

Fig. 1 shows a schematic view on a first side surface of a low gravity lander according to the invention.
Fig. 2 shows a schematic view of the low gravity lander ofFig. 1 viewed from its right side.
Fig. 3 shows a schematic view of the low gravity lander ofFig. 1 viewed from its top side seen inFig. 1 and illustrating the determination of the length of the number of rods with regard to an expected surface roughness.
Fig. 4 shows a schematic view of a low gravity lander according to the invention where the number of rods is in a stowing position.

Fig. 1 shows alow gravity lander 1, comprising a substantially rectangularmain body 10 and alanding device 20 having a number of leg-like rods 21, 22, 23, 24 illustrated in their deployment position. The side wall of themain body 10 illustrated inFig. 1 is afirst side surface 11 corresponding to a front of thelow gravity lander 1. Thefirst side surface 11 has a substantially rectangular shape. However, it is to be understood that the rectangular shape of thefirst side surface 11 is by way of example only. Thelanding device 20 comprises fourrods 21, 22, 23, 24 wherein arespective end 21A, 22A, 23A, 24A is attached to a respective corner of theside surface 11 or an adjacent area of a side wall extending orthogonal to thefirst side surface 11. As can be seen fromFig. 2 which shows thelow gravity lander 1 ofFig. 1 from its right side, an inclination angle α between eachrod 21, 22, 23, 24 and a plane of a first side surface 11 (corresponding to the x-y-plane of the illustrated coordinate system) is substantially 135°. In the shown deployment position of thelanding device 20, therods 21, 22, 23, 24 extend beyond the lateral edges of theside surface 11. The extension of therods 21, 22, 23, 24 is such that the direction of extension is 45° with regard to the axes x, y and z of the coordinate system illustrated inFigs. 1 and 2.
Each of therods 21, 22, 23, 24 is made from a single piece of material, in particular a metal or a metal-alloy. The thickness and the material of therods 21, 22, 23, 24 is such that the rods, in their illustrated deployment position, can bend or buckle under the forces generated by the impact due to a landing on alanding surface 40, thereby absorbing an impact momentum. Hence, the material of therods 21, 22, 23, 24 is such that it is able to transform kinetic energy during the impact at landing into heat.
The length L of therods 21, 22, 23, 24 is determined as a function of the inclination angle (seeFigs. 1 to 3 in which rods are depicted with length L and inclination angle α with regard to the first side surface 11) and an expected roughness of the landing surface such that no part of the landing surface is supposed to contact the main body of thelow gravity lander 1 before therods 21, 22, 23, 24 have buckled or bent. As can be seen from the side view ofFig. 3 which illustrates thelow gravity lander 1 in a landing position on alanding surface 40, thelanding surface 40 has one ormore elevations 41 which are directed to thefirst side surface 11. Thelanding surface 40 can be determined in front of a mission of a low gravity lander.
The smaller the inclination angle α is the bigger the distance between thefirst side surface 11 and thelanding surface 40 can be achieved. However, due to the resulting geometry of the landing device, the behavior of therods 21, 22, 23, 24 might get stiffer. On the other hand, the larger the inclination angle α gets, the smaller the distance between the first side surface and thelanding surface 40 gets. Thus, the danger of a contact of themain body 10 and anelevation 41 of thelanding surface 40 rises. However, the stiffness of thelanding device 20 and itsrods 21, 22, 23, 24 is reduced.
The length of the rods is further determined as a function of the stowage space such that, in a stowage position as illustrated inFig. 4, the rods do not extend beyond thefirst side surface 11 of themain body 10.
The thickness and material of therods 21, 22, 23, 24 are determined by the already chosen length L and by the expected impact momentum, i.e. the product of the total mass of thelow gravity lander 1 and its impact velocity. The thicker therods 21, 22, 23, 24 are the stiffer is their behavior resulting in a higher impact momentum.Hollow rods 21, 22, 23, 24 may be used for mass savings resulting in a reduced impact velocity.
Where a soft terrain of thelanding surface 40 is expected, respective free ends 21E, 22E, 23E and 24E can be bent or fitted with a disc (not shown) to increase the area of contact. However, in the case of therods 21, 22, 23, 24 penetrating the soft terrain, this absorbs as much momentum as the rods are buckling or bending. As a result, the design of therods 21, 22, 23, 24 can be made compliant with various surface properties.
Fig. 4 shows thelow gravity lander 1 with thelanding device 20 in a stowing position of itsrods 21, 22, 23, 24. By folding downrods 22 and 23 overrods 21 and 24, all fourrods 21, 22, 23, 24 on thefirst side surface 11 of themain body 10 can be secured by a single hold downpoint 30. The hold down point may be a launch lock which is able to prevent premature deployment of the rods from its stowing position inFig. 4 to its deployment position inFigs. 1 to 3. Premature deployment of therods 21, 22, 23, 24 has to be prevented before ejection of thelow gravity lander 1 from a mother spacecraft. Thelaunch lock 30 may be opened immediately prior to the ejection of the low gravity lander. A time release device such as a bimetallic or shape memory alloy may be used which secures the rods for a predetermined time (on the order of minutes) upon a triggering event. Upon triggering the bimetallic or shape memory alloy may be preheated before ejection which then frees therods 21, 22, 23, 24 after cooling down. The time span between preheating should be sufficient to eject the low gravity lander from the mother spacecraft.
Therods 21, 22, 23, 24 can be deployed either by their own resilience or with respective additional deployment springs. In the latter, eachrespective end 21A, 22A, 23A, 24A is attached to themain body 10 with a hinge with only one degree of freedom.
If thelow gravity lander 1 needs to self-right itself after the impact of thelanding surface 40 it may jettison therods 21, 22, 23, 24 after impact. Alternatively, therods 21, 22, 23, 24 can be equipped with a predetermined breaking point close to its attached end to the main body (i.e. the attached ends 21A, 22A, 23A, 24A).
The landing device described is vastly simpler, lighter and less costly than alternative landing systems. The landing device can be fitted even on miniaturized landers. It tolerates all surface properties and most topologies.
As an advantage, spacecrafts deploying a low gravity lander as described are no longer required to approach dangerously close to the target bodies, such as a comet or a planet.
Reference list

1: low gravity lander
10: main body
11: first side surface
12: second side surface (being arranged opposite to the first side surface)
20: landing device
21: rod of a first pair of rods
22: rod of a second pair of rods
23: rod of a second pair of rods
24: rod of a first pair of rods
21E: free end ofrod 21
22E: free end ofrod 22
23E: free end ofrod 23
24E: free end ofrod 24
21A: tomain body 10 attached end ofrod 21
22A: tomain body 10 attached free end ofrod 22
23A: tomain body 10 attached free end ofrod 23
24A: tomain body 10 attached free end ofrod 24
30: launch lock
40: landing surface
41: elevation
L: length ofrods 21, 22, 23, 24
α: Inclination angle

Claims

A landing device for a low gravity lander (1) having a main body (10), the landing device comprising a number of leg-like rods (21, 22, 23, 24) , the number of leg-like rods (21, 22, 23, 24) being attachable to a common first side surface (11) of the main body (10), wherein, in the deployment position of the rods (21, 22, 23, 24), each of the number of rods (21, 22, 23, 24) is inclined with regard to a plane of the first side surface (11) of the main body (10) such that the rods substantially extend in a direction of movement of the low gravity lander (1), and wherein the number of rods (21, 22, 23, 24) is made such that they bend or buckle under forces within a predetermined range by an impact due to a landing on a landing surface (40), thereby absorbing an impact momentum,characterised in that the number of leg-like rods is deployable from a stowage position to a deployment position during a landing process.
The landing device according to claim 1, wherein the number of rods (21, 22, 23, 24) is greater than 3, and in particular equals 4.
The landing device according to claim 1 or 2, wherein the length of the rods (21, 22, 23, 24) is determined as a function of the stowage space such that, in the stowage position, the rods (21, 22, 23, 24) do not extend beyond the first side surface (11) of the main body, wherein, in the stowage position, the number of rods (21, 22, 23, 24) are stowed above each other such that they substantially extend parallel to the plane of the first side surface (11).
The landing device according to one of the preceding claims, wherein the inclination angle of the number of rods is in a range between 120° and 150°, in particular 135°.
The landing device according to claim 4, wherein the number of rods (21, 22, 23, 24) extends, in the deployment position, beyond the lateral edges of the first side surface (11).
The landing device according to one of the preceding claims, wherein the number of rods (21, 22, 23, 24) is hollow.
The landing device according to one of the preceding claims, wherein the thickness and/or material of the number of rods (21, 22, 23, 24) is determined as a function of the expected impact momentum.
The landing device according to one of the preceding claims, wherein a free end of at least some of the number of rods (21, 22, 23, 24) is bent.
The landing device according to one of the preceding claims, wherein a free end of at least some of the number of rods (21, 22, 23, 24) is fitted with a disc.
The landing device according to one of the preceding claims, wherein the number of rods (21, 22, 23, 24) is deployable by a swiveling mechanism.
The landing device according to one of the preceding claims, wherein, in the stowing position, the number of rods (21, 22, 23, 24) is held/locked by a single hold down device.
The landing device according to one of the preceding claims, wherein the landing device comprises an activatable launch lock to prevent premature deployment, the launch lock being a time release device which enables a deployment of the number of rods (21, 22, 23, 24) from their stowage position to their deployment position upon a triggering event.
The landing device according to one of the preceding claims, wherein the main body (10) comprises a second side surface (12) being arranged opposite to the first side surface (11) of the main body (10), wherein a further number of leg-like rods is assigned to or attached to the second side surface (11).
A low gravity lander (1) comprising a main body (10) and a landing device according to one of the preceding claims.